EP2593643B1 - Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement - Google Patents

Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement Download PDF

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Publication number
EP2593643B1
EP2593643B1 EP11735628.7A EP11735628A EP2593643B1 EP 2593643 B1 EP2593643 B1 EP 2593643B1 EP 11735628 A EP11735628 A EP 11735628A EP 2593643 B1 EP2593643 B1 EP 2593643B1
Authority
EP
European Patent Office
Prior art keywords
exhaust gas
diffuser
wall
flow
guiding element
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP11735628.7A
Other languages
German (de)
English (en)
Other versions
EP2593643A1 (fr
Inventor
Marc Bröker
Tobias Buchal
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP11735628.7A priority Critical patent/EP2593643B1/fr
Publication of EP2593643A1 publication Critical patent/EP2593643A1/fr
Application granted granted Critical
Publication of EP2593643B1 publication Critical patent/EP2593643B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex

Definitions

  • the invention relates to an exhaust gas diffuser for a gas turbine, having an annular outer wall for guiding the diffuser flow, in which an outer wall concentrically arranged annular guide element for influencing the diffuser flow is provided. Furthermore, the invention relates to a method for operating a gas turbine with an exhaust gas diffuser of the aforementioned type.
  • Gas turbines and the exhaust diffusers used for these are known from the prior art for the longest time.
  • This rather large opening angle is achieved by providing in the center of the diffuser channel an axially extending guide body for extending an otherwise short gas turbine hub.
  • the exhaust gas diffuser is designed as a ring diffuser.
  • larger areas are avoided by
  • the known short gas turbine hubs usually end immediately behind the turbine-side bearing of the gas turbine rotor. However, they have particularly large backflow zones. However, the short gas turbine hubs are also particularly inexpensive.
  • an exhaust gas diffuser which has a concentric to the outer wall annular guide element inside.
  • the guide element is designed such that between the outer wall and the guide element, a nozzle channel is formed, by means of which the wall near flow can be accelerated. This makes it possible, downstream of the guide element to avoid near wall flow separation.
  • influencing the flow in the center of the exhaust gas diffuser, where backflow can occur, is not possible with the aid of the guide element.
  • the invention has for its object to provide a space-saving exhaust diffuser for a gas turbine, which avoids flow separation and/strömzonen for each operating condition of the gas turbine and achieve safe operation of the gas turbine downstream boilers and afterburner for each operating state of the gas turbine while achieving the highest possible efficiency of the gas turbine ,
  • Another object of the invention is to provide a method for operating a gas turbine with an exhaust gas diffuser.
  • the exhaust gas diffuser according to the invention for a gas turbine has an annular outer wall for guiding the diffuser flow, in which an annular guide element arranged concentrically to the outer wall is provided for influencing the diffuser flow, wherein a radially inwardly directed surface of the guide element forms a circumferential, convex contour in longitudinal section for formation a displacement element and the guide element is axially displaceable between two positions, such that the guide element in a first position allows a flow between the guide element and the outer wall and in a second position prevents flow between the guide element and the outer wall.
  • the method according to the invention for operating a gas turbine with an exhaust gas diffuser provides that, as the mass flow through the gas turbine increases, the guide element in the direction of the second position or up to the second position and / or when reducing the mass flow, the guide element in the direction of the first position or until is moved to the first position.
  • the invention is based on the finding that at low mass flows, as they occur on hot days and partial load operation in the gas turbine, the main portion of the mass flow in the exhaust gas diffuser of the gas turbine to the outside, ie towards the outer wall, relocated, so that it to a very pronounced and long backflow zone behind the hub comes.
  • For large mass flows, such as occur on cold days or at full load the majority of the mass flow shifts towards the inside, ie to the hub or to the center. This reduces the proportion of the flow, which is close to the outer wall, resulting in flow separation at the Outside wall can lead.
  • the invention combines two measures in an unforeseeable way.
  • the guide element is designed axially displaceable, whereby the distance between the guide element and outer wall is adjustable. As the distance increases, a greater portion of the flow can be diverted toward the outer wall, reducing the likelihood of near-wall flow separation.
  • the guide element on its inwardly directed surface on a circumferential, convex contour in longitudinal section to form a displacement element. This gives the inner contour of the annular guide element in the form of a Laval nozzle.
  • the diffuser flow captured by the guide element is deflected more towards the hub or toward the diffuser center. This applies all the more, the greater the relative area fraction of the circular opening of the guide element is in relation to the position-dependent flow-through cross-sectional area of the exhaust gas diffuser per se.
  • the guide element arranged in the second position-the guide element bears against the outer wall-the cross-sectional area of the exhaust gas diffuser corresponds to the cross-sectional area of the guide element.
  • the ratio is thus equal to 1.
  • the invention is thus based on the unexpected finding that, despite the use of an inwardly directed constriction, strengthening of the near-wall current is possible. Accordingly, with the solution according to the invention the efficiency of the exhaust gas diffuser can be improved independently of the size of the mass flow, since aerodynamic losses, which are due to relatively large backflow zones or based on near-wall flow separation, are largely avoided.
  • the displacement element when the guide element is arranged in the second position, the displacement element is arranged in that axial section of the exhaust gas diffuser, in which a hub body arranged in the center of the exhaust gas diffuser ends axially. Due to the end of the hub body arranged in the center, return flow zones, which can be shortened by means of the constriction arranged on the guide element, are created in its flow shadows. For this purpose, it is necessary that the constriction is located axially immediately downstream of the end of the hub body. Too much axial distance between the end of the hub body and the axial position of the constriction must be avoided in order for the constriction to have the aerodynamically desired effects of displacing a flow rate to the center, i. to the center of the exhaust diffuser - also achieved.
  • a radially outwardly directed surface of the guide element on a portion of the outer wall can be applied flat. Due to the planar contact of the guide element on the outer wall, a minimal gap near the wall is effectively avoided, since the guide element is particularly close to the outer wall is applied. In size too small, and thus ineffective wall currents are thus effectively avoided.
  • the guide element is supported by distributed along the circumference of the outer wall ribs.
  • This arrangement allows a simple construction for supporting the guide element.
  • the ribs are rigidly secured to the outer wall, wherein at the inner end of each rib a drive for axial displacement of the guide element is provided.
  • double-sided acted upon hydraulic piston are provided by means of which the guide element relative to the ribs and thus also with respect to the outer wall can be moved axially.
  • This first variant has the advantage that both ribs and guide element can be designed to be rigid in their dimensions. That neither the diameter of the guide element nor the length of the ribs must be variable in order to ensure the displaceability of the guide element can.
  • the ribs are each articulated on the outer wall and on the guide element, wherein the axis of rotation of the joints extend in the tangential direction of the exhaust gas diffuser.
  • This embodiment has the advantage that the drive for axial displacement of the guide element is displaced from the flow channel of the exhaust gas diffuser in a slightly colder region of the gas turbine, which reduces the requirements for the drive with respect to the temperature resistance.
  • the ribs since the use of a diameter-constant guide element is preferred, in this case, the ribs must be variable in their radial extent. Conveniently, the ribs are then telescopically movable to adjust their length during the displacement of the guide.
  • a stationary gas turbine is equipped with an exhaust diffuser of the aforementioned embodiments.
  • FIG. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a machine axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 surrounds a combustion chamber 17 which is connected to an annular hot gas duct 16 , There four successively connected blade stages 10 form the turbine unit 8. Each blade stage 10 is formed of two blade rings.
  • a hot gas 11 produced in the annular combustion chamber 6 follows in the hot gas duct 16 each of a row of vanes 13 formed by a blade 15 row 14.
  • the vanes 12 are attached to the stator, whereas the blades 15 a row 14 each by means of a disc 19 on the rotor 3 are attached.
  • a generator or a working machine (not shown) is coupled.
  • the exhaust gas housing 9 adjoins the hot gas duct 16.
  • the exhaust gas housing 9 is the inlet-side part of an exhaust gas diffuser 20 of the gas turbine 1.
  • the hot gas channel 16 merges into the flow channel 22 of the exhaust gas diffuser 20.
  • the arranged in the exhaust housing 9 ribs 24 support the turbine-side end of the rotor 3, which is encapsulated by a hub body 26.
  • the hub body 26 ends axially in the flow channel 22 and is arranged in the center of the exhaust gas diffuser 20.
  • the outer boundary of the exhaust diffuser 20 is formed by an outer wall 28 which is circular and concentric with the machine axis 2.
  • the outer wall 28 extends divergently in the flow direction of the diffuser flow 30, which is referred to as hot gas 11 before expansion in the turbine unit 8.
  • FIG. 2 shows a longitudinal section through the inflow-side portion of the exhaust diffuser 20.
  • an axially displaceable guide element 32 is arranged in the axial portion in which the hub body 26 ends axially.
  • the outwardly directed surface of the guide element 32 in this case has the same conicity as the outer wall 28, so that the guide element 32 rests flat against the outer wall 28.
  • the inwardly facing surface 34 of the guide element 32 has a circumferential, concave in longitudinal section contour to form a displacement element. The contour is designed so that the encompassed by the annular guide element 32 flow cross-section is designed in the manner of a Laval nozzle.
  • an inflow-side flow cross-section of the guide element 32 is greater than a minimum flow cross-section of the guide element 32, wherein the outlet-side flow cross section is greater than the inflow-side flow cross section.
  • the minimum flow cross section is located axially between the inflow-side flow cross-section and the outflow-side cross section.
  • the respective flow cross section is always perpendicular to the machine axis 2.
  • FIG. 3 is the identical portion of the exhaust diffuser 20 as in FIG FIG. 2 shown, only the guide element 32 is opposite to in FIG. 2 Position shown shifted in the axial direction.
  • the guide element 32 is located according to FIG. 3 now downstream of the in FIG. 2 shown position. In the FIG. 3 shown position of the guide element 32 is used as the first position of the guide element 32 and in FIG. 2 shown position of the guide element 32 referred to as the second position.
  • annular flow passage 36 through which a part of the diffuser flow 30 can flow, arises between the inner surface of the outer wall 28 and the outwardly facing surface of the guide element 32.
  • the gas turbine 1 is flowed through by rather smaller mass flows of hot gas 11 or exhaust gas 30. Due to the smaller mass flow, a major portion of the exhaust gas flow shifts to the outside, so far it came to a very pronounced and long backflow zone behind the hub body 26. According to the invention it is now provided that the guide element 32 is moved to the second position. As a result, the constriction is comparatively close to the hub body 26. This causes the exhaust gas 30 to be deflected more intensively in the direction of the center axis 2 (30 '), which significantly reduces the backflow region in the axial section behind the hub body 26. This aerodynamically reduces losses, increases the pressure recovery, and even out the velocity and flow profile in the exhaust diffuser 20.
  • the gas turbine is flowed through by a comparatively large mass flow.
  • the guide element 32 in the axial direction moved to a first position. Due to the displacement, the relative obstruction of the flow cross section of the exhaust gas diffuser 20 decreases due to the guide element 32. Furthermore, in this way, the annular flow passage 36 between the outer wall 28 and the outer surface of the guide element 32. The flow through this passage 36 leads downstream of the guide member 32 to a wall jet, which reduces the increased risk of flow separation on the outer wall 28 for this operating condition ,
  • FIG. 4 shows a detail of the drive of the axially displaceable guide element 32.
  • the guide element 32 is held by a plurality of circumferentially distributed along the circumference of the exhaust diffuser 20 ribs 40.
  • Each of the ribs 40 is rigidly secured to the outer wall 28, but in FIG. 4 not shown.
  • the ribs 40 protrude radially into the flow channel 22.
  • hydraulic cylinders 45 are each provided at an inner end 42 of the ribs 40, whose axially displaceable piston 46 are attached to the guide element 32.
  • the piston 46 can be moved in the axial direction, which leads to the displacement of the guide element 32 in the same direction. If necessary, due to the comparatively high Exhaust gas temperatures to be useful cooling of the adjustment and the supply lines for hydraulic oil.
  • the invention provides an exhaust gas diffuser 20 for a gas turbine 1, which has an annular outer wall 28 for guiding the diffuser flow 30, in which an annular guide element 32 arranged concentrically to the outer wall 28 is provided for influencing the diffuser flow 30.
  • the guide element 32 has a radially inwardly directed surface 34 which has a circumferential, in longitudinal section convex contour to form a displacement element and in that the guide element 32 is axially displaceable between two positions, such that the guide element 32 allows a flow between the guide element 32 and the outer wall 28 in a first position and substantially prevents a flow between the guide element 32 and the outer wall 28 in a second position.
  • a method for operating a gas turbine 1 in which, in order to reduce the aerodynamic losses and increase the pressure recovery while increasing the mass flow, the guide element 32 in the direction of the second position or to the second position and / or reducing the mass flow, the guide element 32nd is moved in the direction of the first position or to the first position.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)

Claims (8)

  1. Diffuseur (20) de gaz d'échappement pour une turbine (1) à gaz,
    comprenant une paroi (28) extérieure annulaire pour le guidage du courant (30) de diffuseur, dans laquelle il est prévu, pour influer sur le courant (30) de diffuseur, un élément (32) annulaire de chicanage disposé concentriquement à la paroi (28) extérieure, dans lequel une surface (34) dirigée radialement vers l'intérieur de l'élément (32) de chicanage a, pour la formation d'un élément de refoulement, un contour faisant le tour et convexe en direction longitudinale, caractérisé en ce que l'élément (32) de chicanage peut coulisser axialement entre deux positions et en ce que l'élément (32) de chicanage rend possible, dans une première position, un courant entre l'élément (32) de chicanage et la paroi (28) extérieure et empêche, dans une deuxième position, un courant entre l'élément (32) de chicanage et la paroi (28) extérieure.
  2. Diffuseur (20) de gaz d'échappement suivant la revendication 1,
    dans lequel, lorsque l'élément (32) de chicanage est dans la deuxième position, l'élément de refoulement est disposé dans la partie axiale du diffuseur (20) de gaz d'échappement, dans laquelle une pièce (26), formant moyeu et disposée au centre du diffuseur (20) de gaz d'échappement, se termine axialement.
  3. Diffuseur (20) de gaz d'échappement suivant la revendication 2,
    dans lequel une surface dirigée radialement vers l'extérieur de l'élément (32) de chicanage peut s'appliquer par une surface sur une partie de la paroi (28) extérieure.
  4. Diffuseur (20) de gaz d'échappement suivant l'une des revendications précédentes,
    dans lequel l'élément (32) de chicanage est porté par un certain nombre de nervures (40) réparties sur le pourtour de la paroi (28) extérieure.
  5. Diffuseur (20) de gaz d'échappement suivant la revendication 4,
    dans lequel les nervures (40) sont fixées rigidement à la paroi (28) extérieure et il est prévu, sur une extrémité (42) intérieure d'au moins l'une des nervures (40), un entraînement pour le déplacement axial de l'élément (32) de chicanage.
  6. Diffuseur (20) de gaz d'échappement suivant la revendication 4,
    dans lequel les nervures sont articulées respectivement sur la paroi (28) extérieure et sur l'élément (32) de chicanage, l'axe de rotation de l'articulation s'étendant dans la direction tangentielle du diffuseur (20) de gaz d'échappement.
  7. Turbine (1) à gaz ayant un diffuseur (20) de gaz d'échappement suivant l'une des revendications précédentes.
  8. Procédé pour faire fonctionner une turbine (1) à gaz suivant la revendication 7,
    qui est parcouru par un courant massique de dimension variable,
    dans lequel,
    lorsque le courant massique augmente, on déplace l'élément (32) de chicanage dans la direction de la deuxième position ou jusque dans la deuxième position et/ou,
    lorsque le courant massique diminue, on déplace l'élément (32) de chicanage dans la direction de la première position ou jusque dans la première position.
EP11735628.7A 2010-07-15 2011-07-13 Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement Not-in-force EP2593643B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11735628.7A EP2593643B1 (fr) 2010-07-15 2011-07-13 Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10007333A EP2407638A1 (fr) 2010-07-15 2010-07-15 Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement
EP11735628.7A EP2593643B1 (fr) 2010-07-15 2011-07-13 Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement
PCT/EP2011/061944 WO2012007499A1 (fr) 2010-07-15 2011-07-13 Diffuseur d'échappement pour turbine à gaz et procédé de fonctionnement d'une turbine à gaz équipée d'un diffuseur d'échappement de ce type

Publications (2)

Publication Number Publication Date
EP2593643A1 EP2593643A1 (fr) 2013-05-22
EP2593643B1 true EP2593643B1 (fr) 2014-10-01

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ID=43240602

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10007333A Withdrawn EP2407638A1 (fr) 2010-07-15 2010-07-15 Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement
EP11735628.7A Not-in-force EP2593643B1 (fr) 2010-07-15 2011-07-13 Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10007333A Withdrawn EP2407638A1 (fr) 2010-07-15 2010-07-15 Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement

Country Status (5)

Country Link
US (1) US9297390B2 (fr)
EP (2) EP2407638A1 (fr)
JP (1) JP5551311B2 (fr)
CN (1) CN103003528B (fr)
WO (1) WO2012007499A1 (fr)

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Publication number Priority date Publication date Assignee Title
DE102011118735A1 (de) * 2011-11-17 2013-05-23 Alstom Technology Ltd. Diffusor, insbesondere für eine axiale strömungsmaschine
US9695284B2 (en) 2013-05-17 2017-07-04 Fujifilm Electronic Materials U.S.A., Inc. Polymer and thermosetting composition containing same
EP3023695A1 (fr) * 2014-11-20 2016-05-25 Siemens Aktiengesellschaft Machine à énergie thermique
US10329945B2 (en) * 2015-04-21 2019-06-25 Siemens Energy, Inc. High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry
CN105336516B (zh) * 2015-12-10 2018-02-02 二一三电器(上海)有限公司 转换开关装置
JP6776154B2 (ja) * 2017-02-27 2020-10-28 三菱重工マリンマシナリ株式会社 ラジアルタービン、ラジアルタービンの排気部材
CN107470833B (zh) * 2017-09-26 2023-05-02 宜昌船舶柴油机有限公司 一种燃气轮机排气扩散器焊接工装

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DE1650079A1 (de) * 1967-07-14 1970-08-27 Licentia Gmbh Vorrichtung zur Verbesserung des Wirkungsgrades von stark erweiterten Diffusoren
US3678690A (en) * 1970-07-10 1972-07-25 United Aircraft Corp Convertible composite engine
SU861664A1 (ru) * 1978-11-10 1981-09-07 Харьковский Ордена Ленина Политехнический Институт Им. В.И. Ленина Выхлопной патрубок турбины
SU857516A1 (ru) 1978-11-27 1981-08-23 Харьковский Ордена Ленина Политехнический Институт Им. В.И.Ленина Выхлопной патрубок осевой турбины
JPS63100640A (ja) 1986-10-17 1988-05-02 Hitachi Ltd 光磁気再生装置
JPS63100640U (fr) * 1986-12-19 1988-06-30
US5209634A (en) * 1991-02-20 1993-05-11 Owczarek Jerzy A Adjustable guide vane assembly for the exhaust flow passage of a steam turbine
DE19805115A1 (de) 1998-02-09 1999-08-19 Siemens Ag Abgasdiffusor
JP3999803B2 (ja) * 2006-08-03 2007-10-31 三菱重工業株式会社 ガスタービン
EP1970539A1 (fr) 2007-03-13 2008-09-17 Siemens Aktiengesellschaft Agencement de diffuseur
JP2009103099A (ja) 2007-10-25 2009-05-14 Toshiba Corp 蒸気タービン

Also Published As

Publication number Publication date
WO2012007499A1 (fr) 2012-01-19
CN103003528B (zh) 2015-04-08
RU2013106505A (ru) 2014-08-20
US9297390B2 (en) 2016-03-29
CN103003528A (zh) 2013-03-27
US20130115044A1 (en) 2013-05-09
JP2013531174A (ja) 2013-08-01
JP5551311B2 (ja) 2014-07-16
EP2407638A1 (fr) 2012-01-18
EP2593643A1 (fr) 2013-05-22

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